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    • 53. 发明申请
    • HIGH COMPRESSION GAS TURBINE WITH SUPERHEAT ENHANCEMENT
    • 具有超强度增压的高压气体涡轮机
    • US20080014079A1
    • 2008-01-17
    • US11773273
    • 2007-07-03
    • Hanford Lockwood
    • Hanford Lockwood
    • F01D1/00
    • F02C6/003F02C1/04F02C1/06F02C3/10
    • A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K−1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.
    • 一种用于在高压缩比燃气轮机或航空燃气轮机的压缩机驱动涡轮机的排出处向热处理气体添加过热的系统和方法。 过热将功率输出涡轮机的温度比(T2 / T1)与压力比(P2 / P1)(K-1)/ K 相等,以实现高效绝热的等熵膨胀 跨越功率输出涡轮。 增加的过热有助于发动机的输出功率降低输出功率涡轮机的低效率。 将所有变量汇集在一起​​,以开发适当的过热水平,以获得最低燃油消耗水平的最大功率输出。
    • 54. 发明授权
    • High compression gas turbine with superheat enhancement
    • 具有过热增强功能的高压缩式燃气轮机
    • US07254951B2
    • 2007-08-14
    • US10752868
    • 2004-01-06
    • Hanford N. Lockwood, Jr.
    • Hanford N. Lockwood, Jr.
    • F02C1/06
    • F02C6/003F02C1/04F02C1/06F02C3/10
    • A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K−1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.
    • 一种用于在高压缩比燃气轮机或航空燃气轮机的压缩机驱动涡轮机的排出处向热处理气体添加过热的系统和方法。 过热将功率输出涡轮机的温度比(T2 / T1)与压力比(P2 / P1)(K-1)/ K 相等,以实现高效绝热的等熵膨胀 跨越功率输出涡轮。 增加的过热有助于发动机的输出功率降低输出功率涡轮机的低效率。 将所有变量汇集在一起​​,以开发适当的过热水平,以获得最低燃油消耗水平的最大功率输出。